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From the equation for total lift on a wing,
L = 1/2 p?V2S CL
where 1/2 p?V2 = the dynamic pressure, S is the surface area of the wing, and CL = the coefficient of lift, after some manipulation, it is possible to calculate the minimum flight velocity needed for takeoff or landing Vmin,
The density r ? is considered to be constant and if the weight (W) is considered a fixed characteristic of the airplane, then the only way to reduce the minimum velocity Vmin is to increase CL,max and/or the wing area S. Slots and flaps are used for this purpose.
The maximum coefficient of lift CL,max may be increased through the use of a slot formed by a leading-edge auxiliary airfoil called a slat...
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